Effects of Tip Clearance and Casing Recess on Heat Transfer and Stage Efficency in Axial Turbines
Author:
Affiliation:
1. AYT Corporation, Brook Park, OH 44142
2. Institute for Computational Mechanics in Propulsion (ICOMP), NASA Lewis Research Center, Cleveland, OH 44135
3. NYMA, Inc., NASA Lewis Group, Cleveland, OH 44135
Abstract
Publisher
ASME International
Subject
Mechanical Engineering
Link
http://asmedigitalcollection.asme.org/turbomachinery/article-pdf/121/4/683/5619700/683_1.pdf
Reference23 articles.
1. Ameri, A. A., and Steinthorrson, E., 1995, “Prediction of Unshrouded Rotor Blade Tip Heat Transfer,” ASME Paper No. 95-GT-142.
2. Ameri, A. A., and Steinthorrson, E., 1996, “Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer,” ASME Paper No. 96-GT-189.
3. Ameri A. A. , SteinthorssonE., and RigbyD. L., 1998, “Effect of Squealer Tip on Rotor Heat Transfer and Efficiency,” ASME JOURNAL OF TURBOMACHINERY, Vol. 120, pp. 753–759.
4. Boyle R. J. , HaasJ. E., and KatsanisT., 1985, “Comparison Between Measured Turbine Stage Performance and the Predicted Performance Using Quasi-3D Flow and Boundary Layer Analyses,” J. Propulsion Power, Vol. 1, No. 3, pp. 242–251.
5. Briley, W. R., Roscoe, D. V., Gilbeling, H. J., Buggeln, R. C., and Sabnis, J. S., 1991, “Computation of Flow Past a Turbine Blade With and Without Tip Clearance,” ASME Paper No. 91-GT-56.
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